• Provided for the nose gear offers resistance to shimmy.

• A forged aluminum alloy torque link w/c keep the lower strut aligned with the nose gear steering system.

• The main landing gear is attached to forgings in the landing gear bulkhead structure.

• Consist of 6.00X6 6 ply rating tire, 6.00X6 inner tube and 6.00X6 wheel assy.

• The two magnesium alloy sections of the wheel are bolted together & can be seperated for tire removal

• The single brake disc is secured to the wheel inner section.

• T41B/D consist of 6.00X6 6 ply rating tire, 6.00X6 inner tube and 6.00X6 wheel assy.

• T41K consist of 5.00X5 6 ply rating tire. 5.00X5 inner tube and 5.00X5 wheel assy.

-Located at the back of the rudder pedal.

-It is actuated by applying toe pressure on the rudder pedal.

-Small reservoir is incorporated with each master cylinder.

Consists of housing, piston, pressure plate, back plate, linings riveted on pressure plate and back plate.

IO-360DB21B -

The "I" stands for?

IO-360DB21B -

The "O" stands for?

IO-360DB21B -

The "360" stands for?

IO-360DB21B -

The "DB" stands for?

IO-360DB21B -

The "21" stands for?

IO-360DB21B -

The "B" stands for?

• Fuel enters the fuel pump at the top of the vapor separator swirl chamber where it is centrifuged, separating the liquid from fuel vapors.

• Liquid fuel is forced through the fuel pump inlet vanes which create the necessary differential pressure required to draw fuel into the pump inlet and expel pressurized fuel through the pump outlet.

• Fuel vapors separated in the swirl chamber return to the aircraft fuel tank.

• From the Fuel Injection Pump, fuel is directed to the fuel metering valve which is mounted on the side of the air throttle body.

• The shaft that positions the air throttle body butterfly valve also positions the metering valve.

• The air throttle body valve and metering shaft are linked to the cockpit throttle control.

Contains a diaphragm chamber and necessary outlet ports which connect to the fuel injector lines.

-The spring-loaded diaphragm works with a ported plunger to allow fuel through to the fuel injector lines.

-“air bleed” type fuel nozzles which spray fuel directly into the intake port of the cylinders.

-When the engine is running, flow through the nozzle is continuous and will enter the cylinder combustion chamber when the intake valve opens.

• include the aircraft filter/alternate air door, throttle, manifold and cylinder intake ports.

• a six-tube, air distribution system mounted atop the engine.

• It serves to carry induction air to the individual cylinder intake ports.

• IO-360 engines ignition systems in AETC T-41 use either CMI (Bendix) impulse coupled magnetos in a dual configuration for redundant ignition to each cylinder.

• Dual spark plugs are installed in bosses in each cylinder head.

• The magnetos are installed at the rear of the engine, driven by the crankshaft.

INCLUDES THE OIL SUMP, OIL PUMP, AND PRESSURE RELIEF VALVE

OIL SYSTEM

• attached to the crankcase oil sump and accessory case mounting flanges with bolts, nuts, washers, and lock washers.

• incorporates a threaded boss for a drain plug and copper crush washer to facilitate draining engine oil.

• The drain plug boss has provisions for safety wiring the magnetic drain plug after it has been properly torque.

OIL SYSTEM

• positive displacement oil pump

• consists of two meshed gears that revolve inside the pump housing cavity.

• Incorporated in the accessory housing

OIL SYSTEM

• If oil pressure is beyond the prescribed limits, turning the adjustable screw clockwise increase the oil pressure and vice versa.

• Contain spring and plunger inside

OIL SYSTEM

• As oil enters the oil cooler, it will flow in one of two directions:

• (a) When the oil is cold, the oil temperature control valve (vernatherm) will open and most of the oil will bypass the cooler. Some oil always flows through the cooler to help prevent congealing in cold weather.

(b) As the oil warms, the oil temperature control valve actuates to close off the cooler bypass, forcing oil flow through the cooler core. In operation, the oil temperature control valve modulates to maintain oil

SF260 LEFT AND RIGHT TIP TANK CAPACITY (LITERS)

SF260 LEFT AND RIGHT WING TANK CAPACITY (LITERS)

SF260 LEFT AND RIGHT WING USABLE FUEL (LITERS)

SF260 LEFT AND RIGHT WING TIP USABLE FUEL (LITERS)

3 ELECTRICAL POWER SOURCE

ELECTRICAL SYSTEM COMPONENTS AND OPERATIONS

ž28 volts

ž38 ampere rating

žConnected to the engine through accessory housing

žLead Acid

ž12 Cell

ž24Volts

ž17 ampere-hour

žQuick disconnect fitting

žInstalled in the tail cone aft of baggage compartment

ž28-volt standard AN type receptacle

žUse for cold weather starting or when lengthy electrical maintenance

žWith reverse polarity protection

(Alternating system components)

žGear driven, flange mounted on the engine & is rated at 28 volts, 38 ampere

žPrimary source of electrical power.

(Alternating system components)

žLocated at the upper right of the firewall

žSolid-state.

žRemove & replace item

žNot repairable.

žRegulates the alternator field current.

(Alternating system components)

žLocated at the firewall

žRemove and replace item

žNon- repairable

žOpen the over voltage warning light when the voltage reading is 32 Volts and simultaneously shuts off the alternator

(Alternating system components)

žPress-to-test light

žLocated on the lower right side of the instrument panel

žIlluminate anytime electrical system voltage exceeds approximately 32 volts.

(Alternating system components)

žToggle-type switch

žLocated beside the throttle control lever

žInstalled with a switch guard

žThe function is to apply or remove power to the alternator field circuit.

(Alternating system components)

žLocated on the right side of the instrument panel

žIndicates a charging or discharging condition.

žAlso indicates the flow of electricity, in amperes, from the alternator to the battery or from the battery to the aircraft electrical system.

(BATTERY System components)

ž24Volts

ž17 ampere-hour

žQuick disconnect fitting

žInstalled in the tail cone aft of baggage compartment

(BATTERY System components)

žMounted beside the battery box

žPlunger type contactor

žActuated by the “Master Switch”

(BATTERY System components)

žLocated on the lower switch and control panel

žPush-pull type

žPulled – ON

žPushed – OFF

(BATTERY System components)

žMounted on the lower switch and control panel

žLabeled according to their function and amperage

žPush-to-reset type

žMust cool before it can be reset

žIf the breaker trips after reset, do not attempt to reset again.

•Located at the instrument panel.

•Illuminating when the engine manifested a metal in the oil system.

•Connected to a chip detector plug in the oil drain sump.

•When the fuel drops to 9 gallons in either fuel tank, the sensing unit will illuminate the applicable low fuel warning light.

•Both pilot’s are required a headset to have communication to each other.

•Press to talk are integrated at each control yoke for press to talk function

•Pressing toggle switch fore transmit outside the aircraft and aft for the intercom.

Removal of cabin doors is accomplished either removing the screws which attached the hinges or by removing the jettisonable hinge pins

T41 AIR SPEED LIMITATION

Maximum Allowable (red line):

T41 AIR SPEED LIMITATION

Caution Range (Yellow Arc):

T41 AIR SPEED LIMITATION

Normal Range (Green Arc):

T41 AIR SPEED LIMITATION

Flap Operating Range (white arc):

T41 R172E & H FUEL TANK CAPACITY

T41 R172K FUEL TANK CAPACITY

Allows selection of fuel from various tanks.

It contains three positions: LEFT, RIGHT, and BOTH.

Selecting the LEFT or RIGHT position allows fuel to feed only from that tank, while selecting the

BOTH position feeds fuel from both tanks.

Position may be used to balance the amount of fuel remaining in each wing tank.

•Used to cut-off fuel from the tank to the

engine.

•Located at the floor board of copilot side

Strainer removes moisture and other sediments that might be in the system. Since these contaminants are heavier than aviation fuel, they settle in a sump at the bottom of the strainer assembly.

Sump is a low point in a fuel system and/or fuel tank. The fuel system may contain sump, fuel strainer, and fuel tank drains, some of which may be collocated.

The fuel strainer should be drained before each flight.

Used for engine starting, vapor purging and for engine operation whenever the engine-driven fuel pump fails.

On R172E & H, located at the firewall enclosed by a cooling shroud

On R172K, located at the floorboard beneath the fuel selector valve

It controls the amount of intake air admitted into the intake manifold and meters the proportionate amount of fuel to the fuel manifold valve.

Located at the top of the engine assembly fore of fuel manifold valve

•Serves to provide a clean cut off of fuel to the cylinder when the engine is shut down.

•Located at the top of the engine aft of fuel metering unit.

The injector nozzle ( one per cylinder ) are air bleed type fuel nozzles which spray fuel directly into intake port of the cylinder.

Located at the top of the cylinder beside the spark plugs